Note: Descriptions are shown in the official language in which they were submitted.
CA 02847641 2014-03-27
FUEL SYSTEM OF GAS TURBINE ENGINES
TECHNICAL FIELD
The invention relates generally to gas turbine engines, and more particularly,
to an improved fuel system of gas turbine engines.
BACKGROUND OF THE ART
A gas turbine engine typically includes a fuel system for delivery of fuel
from a fuel source to a combustor where the fuel in combination with
compressed air
is ignited and produces combustion gases to drive the turbine engine. The fuel
is
delivered through the system under a fuel pressure established by a fuel pump.
When
the turbine engine is shut down for any reason, fuel remains in the system.
Fuel,
particularly liquid fuel, in the fuel system can result in gumming, coking,
and similar
disadvantageous results, thereby decreasing the operational life of the
components,
such as fuel nozzles. Furthermore, cold fuel remaining within the fuel system
which
is not under pressure and is un-metered, can interfere with the next turbine
start-up
process. The fuel remaining in the system will eventually be lost through
leakage
from the fuel nozzles, which is not acceptable for ecological reasons and is
not
effectively used for engine operation. Efforts have been made to find methods
of
purging fuel from the fuel system on shutdown of the engine. Conventionally,
fuel
remaining in the system is discharged into the combustor and cannot be reused,
or is
sucked into an ecology valve cylinder to be stored for re-use in the next
engine start-
up process but this requires a complicated system structure and compromises
the
performance reliability of the fuel system and adds weight.
Accordingly, there is a need to provide an improved fuel system of gas
turbine engines.
SUMMARY OF THE INVENTION
It is therefore an object of this invention to provide a fuel system of gas
turbine engines and a method for operating a fuel system of gas turbine
engines,
overcoming the disadvantages of the prior art.
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In one aspect, the present invention provides a method for purging fuel from
a fuel system of a gas turbine engine on shutdown of the engine, comprising:
terminating a fuel supply to the fuel system on shutdown of the engine; and
using
residual compressed air in a combustor of the engine to create a reversed
pressure
5 differential in contrast to a forward pressure differential of the fuel
system when the
engine is in operation, and under the reversed pressure differential
substantially
purging the fuel remaining in the system therefrom to the fuel source.
In another aspect, the present invention provides a liquid fuel reverse purge
control system for a fuel manifold of a gas turbine engine comprising a fuel
pump for
10 pressurizing fuel from a fuel source; a fuel manifold in fluidic
communication with a
compressor stage of the engine; a fluidic connection between the fuel pump and
the
fuel manifold for controllable delivery of fuel from the fuel source to the
fuel
manifold, the fluidic connection having a fuel purge passage and a first
control valve
associated therewith to selectively open and close the fuel purge passage; and
a
15 control unit in controlling contact with the first control valve to open
the fuel purge
passage on shutdown of the engine, thereby allowing residual compressor air
diverted
to the fuel manifold to force fuel to flow back from the fuel manifold through
the
fluidic connection to the fuel source.
In another aspect, the present invention provides a method for operating a
20 fuel system of a gas turbine engine, comprising pumping a fuel flow from
a fuel
source through a first section of the system to a pilot torch nozzle for pilot
torch
ignition; pumping a fuel flow from the fuel source through a second section of
the
system to a manifold of a combustor of the engine for combustion; and wherein
a
pressure differential between the first and second sections is monitored as a
reference
25 signal.
In a further aspect, the present invention provides fuel system of a gas
turbine engine comprising a fuel pump for pressurizing fuel from a fuel
source; a
pilot torch nozzle in fluidic communication with a compressor stage of the
engine; a
fuel manifold of a combustor in fluidic communication with the compressor
stage of
30 the engine; a fluidic connection extending from the fuel pump and
dividing into at
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=
least first and second sections thereof to connect the respective pilot torch
nozzle and
the fuel manifold; a control unit in electrical contact with the fluidic
connection for
controllably operating the fuel system; and a differential pressure transducer
between
the first and second sections of the fluidic connection for monitoring a
pressure
5 differential therebetween as a reference signal to be used by the control
unit.
Further details of these and other aspects of the present invention will be
apparent from the detailed description and drawings included below.
DESCRIPTION OF THE DRAWINGS
Reference is now made to the accompanying figures depicting aspects of the
10 present invention, in which:
Figure 1 is a schematic cross-sectional view of a turbofan gas turbine engine
as an example illustrating an application of the present invention;
Figure 2 is a schematic illustration of a fuel system used for the engine of
Figure 1, showing one embodiment of the present invention;
15 Figure 3 is a schematic illustration of the fuel system of Figure 2,
showing a
step of the fuel system operation for supplying a torch flow to a pilot torch
nozzle
while a main manifold is in a dry condition;
Figure 4 is a schematic view of the fuel system of Figure 2, showing another
step of the fuel system operation for supplying both torch and manifold flows
under a
20 low fuel pressure to the respective pilot torch nozzle and the main
manifold of the
combustor;
Figure 5 is a schematic view of the fuel system of Figure 2, showing a
further step of the fuel system operation, similar the step of Figure 3, but
with the
main manifold refilled with the fuel;
25 Figure 6 is a schematic illustration of the fuel system of Figure 2,
showing a
further step of the fuel system operation for supplying both the torch flow
and main
manifold flow under a high fuel pressure to the respective pilot torch nozzle
and the
main manifold of the combustor;
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Figure 7 is a schematic illustration of the fuel system of Figure 2, showing a
further step of the fuel system operation for reverse purging of fuel from the
pilot
torch nozzle;
Figure 8 is a schematic illustration f the fuel system of Figure 2, showing a
further step of the fuel system operation for reverse purging of fuel from the
main
manifold of the combustor; and
Figure 9 is a schematic illustration of the fuel system, showing the
embodiments thereof, alternative to the embodiment of Figure 2.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
Referring to Figure 1, a turbofan gas turbine engine incorporating an
embodiment of the present invention is presented as an example of the
application of
the present invention, and includes a housing or nacelle 10, a core casing 13,
a low
pressure spool assembly seen generally at 12 which includes a fan assembly 14
and a
low pressure turbine assembly 18, and a high pressure spool assembly seen
generally
at 20 which includes a compressor assembly 22 and a high pressure turbine
assembly 24. The core casing 13 surrounds the low and high pressure spool
assemblies 12 and 20 in order to define a main fluid path (not indicated)
therethrough. In the main fluid path there are provided a combustor seen
generally
at 25 and a fuel system 28 for delivery of fuel to the combustor 25 for
combustion.
The compressor assembly 22 provides a compressed airflow (not indicated)
through
the main fluid path and in communication with the combustor 25 for combustion
therein.
Referring to Figures 1 and 2, the fuel system 28 according to one
embodiment of the present invention, comprises a fuel pump 30 (a vane type of
fuel
pump is preferred, which is driven independent of the high pressure spool) for
pressurizing the fuel to establish a fuel pressure under which fuel is
delivered from a
fuel source 32 through a fluidic connection of the fuel system 28 preferably
to at least
one pilot nozzle such as a torch nozzle 34 or some other form of primary
nozzle,
which is used to initialize ignition of combustion in the combustor 25, and a
main
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manifold 36 of the combustor 25 which distributes fuel to fuel nozzles of the
combustor 25 in order to supply fuel for combustion within the combustor 25.
The
main manifold 36 is in fluid communication with the combustion chamber which
in
turn is in a fluidic communication with a stage of the compressor 22. The
fluidic
connection of the fuel system 28 further includes, for example, a minimum
pressure/
flow divider valve 38 having an inlet 40 and outlets 42, 44, which are
normally
closed under a spring force of the minimum pressure/flow divider valve 38. The
minimum pressure/flow divider valve 38 is adapted to open the outlet 42 only
when
inlet 40 is exposed to a low pressure which is equal to or above a
predetermined
minimum pressure threshold, but is lower than a predeteremined high pressure
threshold, or to open both outlets 42 and 44 when inlet 40 is exposed to a
high
pressure, which is equal to or above the predetermined high pressure
threshold. This
will be further discussed with reference to the system operation process.
A fuel flow passage 46 interconnects the fuel pump 30 and the inlet 40 of the
minimum pressure/flow divider valve 38, and a fuel flow passage 48 is
connected
between the outlet 42 and the pilot torch nozzle 34. There is a fuel flow
passage 50
extending between the outlet 44 of the minimum pressure /flow divider valve 38
and
the main manifold 36 in a parallel relationship with the fuel flow passage 48.
It
should be noted that due to the flow rate difference between the required fuel
flow to
the pilot torch nozzle 34 (the torch flow) and the fuel flow to the main
manifold 36
(the manifold flow), the fuel flow passage 48 is sized in cross-section
smaller than
the fuel flow passage 50, thereby resulting in a high flow resistance of the
fuel flow
passage 48 relative to the fuel flow passage 50.
A differential pressure transducer 52 is preferably connected between the
fuel flow passage 48 and the fuel flow passage 50 such that a pressure
differential
between fuel flow passages 48 and 50 can be monitored from time to time and
particularly during engine start up while no fuel flow is delivered to the
main
manifold 36. The differential pressure transducer 52 is electrically connected
to an
electrical engine control (EEC) 60 such that the pressure differential between
the fuel
flow passages 48 and 50 monitored by the differential pressure transducer 52,
can be
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used by EEC 60 as a reference signal for controlling the operation process of
the fuel
system 28.
In practice, metering the start fuel flow using only the fuel pump
characteristics is not very practical. However, when the pressure differential
between
the pilot nozzle fuel supply and the main manifold (which is in communication
with
the combustor chamber pressure) is measured, the fuel flow to the pilot nozzle
can be
calculated and thus controlled by adjusting the speed of the fuel pump via the
EEC.
A flow equalization solenoid valve 58 is preferably connected by fuel flow
passages 54, 56 to the respective fuel flow passages 48 and 50, in a parallel
relationship with the differential pressure transducer 52. The flow
equalization
solenoid valve 58 is a normally open valve to allow a fluidic communication
between
the fuel flow passages 48 and 50 when the minimum pressure/flow divider valve
38
closes outlets 42 and 44 thereof. The flow equalization solenoid valve 58 is
electrically connected to and controlled by EEC 60 and is adapted to close the
fuel
flow passages 54, 56 when a control signal is received from the EEC 60.
The differential pressure transducer 52 is in fluidic connection with the
respective pilot torch nozzle 34 and the main manifold 36 which are in turn in
fluid
communication with the combustion chamber, which is supplied with air pressure
from the compressor, for example, P3 compressor air. Therefore, the P3
compressor
air pressure is automatically provided to the differential pressure transducer
52 as a
reference pressure via fuel flow passage 50, when the flow equalization
solenoid
valve 58 is in the closed position and outlet 44 of the minimum pressure/flow
divider
valve 38 is closed (when the compressor 22 is rotated either by the turbine 24
or by a
starter) for monitoring the pressure differential between the fuel flow
passages 48 and 50. For example, the pressure differential between the fuel
flow
passages 48 and 50 monitored by the differential pressure transducer 52, can
be used
for monitoring a fuel flow through the fuel flow passage 48 to the pilot torch
nozzle 34 during the engine start-up process, and to determine when to
deactivate the
flow equalization solenoid valve 58 to open the fuel flow passages 54, 56 in
order to
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allow the fuel flow to pass through the fuel flow passage 50 to the main
manifold 36.
This will be further described hereinafter.
An ecology solenoid valve 62 is preferably provided to control fuel flow
passages 64, 66 which are connected to the respective fuel flow passages 46
and 48 to
form a bypass over the minimum pressure/flow divider valve 38. The ecology
solenoid valve 62 is normally closed and is electrically connected to EEC 60.
The
ecology solenoid valve 62 can be controlled by EEC 60 to selectively open for
establishing the fluidic connection of the fuel system 28 between the fuel
source 32
and the main manifold 36 as well as the pilot torch nozzle 34 when required.
A check valve 68 is preferably provided within the fuel flow passage 66.
Should the ecology valve 62 be opened in malfunction, the check valve 68
ensures
that the bypass connection over the minimum pressure/flow divider valve 38
should
be used only for fuel flowing therethrough back to the fuel pump 30 and the
fuel
source 32, but not for fuel supply therethrough from the fuel pump 30.
Figures 3-8 illustrate the steps of operation of the fuel system 28. For
convenience of description, different numerals in those Figures are used in
connection with arrows to indicate fluid flows under pressure differentials
having
different values. A single head arrow indicates the direction of the fluid
flow and a
double head arrow indicates the fluid flow is blocked.
Referring to Figure 3, EEC 60 controls the fuel pump 30 to operate at a
speed to establish the low fuel pressure during engine start conditions. The
low fuel
pressure forces the minimum pressure/flow divider valve 38 to open the inlet
40 and
outlet 42, allowing a fuel flow indicated by arrow 70 to pass through the fuel
passages 46, 48 to the pilot torch nozzle 34. The ecology solenoid valve 62 is
normally closed such that there is no fuel flow through the bypass formed by
the fuel
flow passages 64, 66. The flow equalization solenoid valve 58 is activated by
EEC 60 to be closed during the initial engine start condition such that there
is no fuel
flow passing through fuel flow passage 50 to the main manifold, either via the
minimum pressure/flow divider valve 38 or via the fuel flow passages 54, 56.
The
fuel flow passage 50 and the main manifold 36 may either remain in a dry
condition
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(or be pre-filled with fuel), having a pressure therein equal to the air
pressure in the
combustor 25 of Figure 1. The air (or the pre-filled fuel) inside of the fuel
flow
passage 50 and the main manifold 36 under such air pressure, is indicated by
the
hollow double-head arrows 72. The low fuel pressure in the fuel flow
passages 46, 48 is higher than the pressure in the fuel flow passage 50,
thereby
forming a pressure differential therebetween. The pressure differential is
monitored
by the differential pressure transducer 52 which sends corresponding signals
to
EEC 60.
Referring to Figure 4 and 5, the flow equalization solenoid valve 58 is
preferably deactivated to temporarily open the fuel flow passages 54, 56
during the
low fuel pressure start condition of the engine, to allow the fuel to flow
through the
fuel flow passages 54, 56 and 50 into the main manifold 36 until the main
manifold 36 and the fuel flow passage 50 are filled up with fuel, and then the
flow
equalization solenoid valve 58 is activated to close the fuel flow passages
54, 56, as
shown in Figure 5.
When the fuel flow passages 54, 56 are temporarily open, the fuel pump 30
is controlled by EEC 60 to operate at a higher speed to provide a fuel flow at
a high
rate for the required fuel volume to both the pilot torch nozzle 34 and the
main
manifold 36, while maintaining the low fuel pressure for the appropriate
operation of
the minimum pressure/flow divider valve 38, in order to ensure that the main
manifold fill-up process is under control.
The pressure differential between the fuel flow passages 48 and 50 which is
monitored by the differential pressure transducer 52, varies during the
process of the
main manifold fill-up. The differential pressure transducer 52 detects when
the main
manifold 36 and the fuel flow passage 50 are filled up with fuel because a
pressure
pulse will occur when all of the air has been expelled from the main manifold
36 and
the fuel flow passage 50 which will act in a specific direction on the
differential
pressure transducer 52. The flow equalization solenoid valve 58 is then
activated by
EEC 60 to close, thereby blocking the fuel flow to the main manifold 36.
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..
After the main manifold 36 and the fuel flow passage 50 are filled up with
..
fuel and the fuel flow passages 54 and 56 are closed by the flow equalization
solenoid valve 58, as shown in Figure 5, the fuel remaining in the fuel flow
passage 50 under a fuel pressure, as indicated by double-head broken arrows
74, is
5 exposed to and the pressure thereof is equal to the P3 compressor air
because the
compressor 22 of Figure 1 is rotated by an engine starter although the engine
is not
being operated by combustion gases at this moment.
In Figure 6, during the engine start-up the pilot torch from the pilot torch
nozzle 34 is lit up, and upon which EEC 60 commands the fuel pump to increase
the
10 pump drive to establish a higher fuel pressure in order to force the
minimum
pressure/flow divider valve 38 to open both outlets 42 and 44 which results in
a
gradual and controlled increase in the fuel flow, as the compressor speed
increases.
Meanwhile, EEC 60 commands the flow equalization solenoid valve 58 to open the
fuel flow passages 54, 56, thereby allowing fuel flow via both outlets 42, 44
through
15 the fuel flow passage 50 to the main manifold 36 for establishing a
properly
distributed fuel flow between all nozzles and a stable combustion process in
the
combustor 25 of Figure 1. At the same time, fuel flow 76 moves via outlet 42
of the
minimum pressure/flow divider valve 38 through the fuel flow passage 48 to the
pilot
torch nozzle 34 to maintain the pilot torch. This process will be maintained
during
20 engine operation for a stable combustion in the engine combustor 25.
The check valve 68 in fuel flow passage 66 does not allow fuel flow from
the fuel pump 30 to pass the bypass formed by the fuel flow passages 64, 66,
to the
fuel flow passage 48. EEC 60 also commands the ecology solenoid valve 62 to
close
the bypass. Therefore, during engine start-up and the entire engine operation
process,
25 fuel is supplied from the fuel source 32 to the respective fuel torch
nozzle 34 and the
main manifold 36 through the fluidic connection of the fuel system 28 via the
minimum pressure/flow divider valve 38, but not via the closed bypass of fuel
flow
passages 64, 66.
Referring to Figure 7, on a commanded shutdown sequence, the fuel
30 pump 30 is shut off, causing fuel pressure at the inlet 40 of the
minimum
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..
_ .
pressure/flow divider valve 38 to drop lower than the predetermined minimum
..
pressure threshold or to zero. Thus, the minimum pressure/flow divider valve
38
under the spring force thereof is returned to a closed position, thereby
closing inlet 40
and outlets 42, 44. Meanwhile, at a pre-determined compressor speed EEC 60
5 commands the ecology solenoid valve 62 to be activated to open the bypass
formed
by the fuel flow passages 64, 66 and the flow equalization solenoid valve 58
to be
activated to close the fuel flow passages 54, 56.
At this moment, the residual compressed air from the compressor 22 of
Figure 1 has a relatively high residual pressure value and is in fluidic
communication
10 with the system 28 via the pilot torch nozzle 34 and the main manifold
36, thereby
creating a reversed pressure differential in the fuel system 28, in contrast
to the fuel
pressure differential in the fuel system 28 established by the fuel pump 30
for
supplying fuel to the respective pilot torch nozzle 34 and the main manifold
36, as
previously described with reference to Figures 3-6. The fuel remaining in the
pilot
15 torch nozzle 34 is forced by such a reversed pressure differential, to
flow back
through the fuel flow passage 48, the bypass of fuel flow passages 66, 64, the
fuel
flow passages 46 and the fuel pump 30, and into the fuel source 32. At this
time, the
fuel remaining in the main manifold 36 under the same reversed pressure
differential,
cannot flow back to the fuel source 32 through the fluidic connection of the
fuel
20 system 28 because the fuel flow passages 54, 56 which are connected to
the
respective fuel flow passages 48 and 50, have been closed by the flow
equalization
solenoid valve 58, and fluidic communication between the fuel flow
passages 48 and 50 via the minimum pressure/flow divider valve 38 has also
been
blocked by the closed position of this valve. Broken line arrows 78 illustrate
the fuel
25 flow in the fuel system 28 under the reversed pressure differential
having a relative
high value created by the residual compressor air. Single head arrows 78
indicate the
flow direction and double head arrows 78 indicate that the fuel flow is
blocked.
Referring to Figure 8, after a relatively short time delay from the moment of
engine shutdown, the reversed pressure differential in the fuel system 28
changes to a
30 relatively low value due to the residual compressor air pressure drop as
the
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compressor speed reduces. Nevertheless, the reversed pressure differential in
the fuel
system 28 with the relatively low value is still sufficient to substantially
purge the
fuel from the fuel system 28. At this moment, EEC 60 commands the flow
equalization solenoid valve 58 to open the fuel flow passages 54, 56 to
fluidically
connect the fuel flow passage 48 and 50. Thus, the fuel remaining in the main
manifold 36 and fuel flow passage 50 can be forced by the reversed pressure
differential in the fuel system 28, to flow through the fuel flow
passages 56, 54, 48, 66, 64 and 46 and the fuel pump 30, into the fuel source
32. The
ecology solenoid valve 62 remains activated and flow equalization solenoid
valve 58
remains deactivated to open the fluidic connection of the fuel system 28 in
order to
allow fuel to be substantially purged from the pilot torch nozzle 34 and the
manifold 36, before the residual compressor air pressure drops to zero. Broken
line
arrows 78 are used to indicate fuel flow under the reversed pressure
differential
having a relatively low value.
Such a time delay to begin purging the fuel from the main manifold is
preferable because the fuel flow from the pilot torch nozzles 34 through the
fluidic
connection of the fuel system 28 confronts relatively high resistance in
contrast to the
flow resistance of the fuel flow from the main manifold 36 through the fluidic
connection of the fuel system 28 to the fuel sources 32. Therefore, the
reversed
pressure differential having a high level is preferred in order to
substantially purge
the fuel from the pilot torch nozzles 34.
It should be noted that the fuel flow under the reversed pressure differential
is forced to pass through the fuel pump 30 to the fuel source 32. Therefore,
the fuel
pump 30 is preferably of a type having a relatively high leakage volume when
the
fuel pump 30 is not in operation, such as a vane type. However, if a fuel pump
having a low leakage volume in non-operative conditions is used, such a fuel
pump
may be driven in a reversed rotational direction at a low speed to facilitate
the passing
through of the fuel during the fuel purging process, but not for performing a
vacuum
pump function.
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,
. .
When the fuel purging process is completed (which may be determined by
..
differential pressure transducer 52 signals or simply by a time lapse), EEC 60
commands both the ecology solenoid valve 62 and the flow equalization solenoid
valve 58 to be deactivated such that the ecology solenoid valve 52 is closed
and the
equalization solenoid valve 58 is open, as illustrated in Figure 2.
It should be noted that a relatively low range (i.e. sensitive) pressure
transducer is preferred for the purpose of monitoring flow during start and
fuel pulses
on manifold filling. It is preferable to use a sensitive or low range pressure
transducer
in practical terms in the embodiment of the present invention because the
transducer
never has a high pressure differential applied to it. The differential
pressure is
shunted out via fuel passages 54 and 56 in conjunction with flow equalization
valve 58, limiting the maximum differential pressure to which the transducer
is
exposed. For example, the differential pressure during start is of the order
of 100 PSI
maximum, however the fuel system pressure may be over 1000 PSI during take off
conditions. A transducer used for applications involving 1000 PSI is very poor
at
resolving small pressure differentials needed to control flow at low flow
conditions.
Therefore, it is preferable to have a transducer having a maximum pressure
indication
for example, not greater than 120 PSI.
In Figure 9, a schematic illustration is used to show in principle an
alternative embodiment of the present invention which may not be a complete
system
and may need more components to be included in a practical view point. Fuel
system 128 is a simplified version of the fuel system 28 of Figure 2. Similar
components are indicated by similar numeral references and will not be
redundantly
described herein. The fuel system 128 is implemented by omission of the bypass
including the fuel flow passage 64, 66 with the ecology solenoid valve 62 and
the
check valve 68, or by omission of both that bypass and the fluidic connection
between the fuel flow passages 48 and 50, including the fuel flow passages 54,
56
and the flow equalization solenoid valve 58, as shown in broken lines in
Figure 9.
Furthermore, as a result of such omissions, the minimum pressure/flow divider
valve 38 of the fuel system 28 of Figure 2 is replaced by, for example, an EEC-
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. CA 02847641 2014-03-27
,
. _
controlled flow divider solenoid valve 138, having inlet 140 and outlets 142
and 144.
..
The valve 138 is operated on the commands of EEC 60 rather than by the
pressure
changes at inlet 140.
During engine start-up and operating conditions, fuel is driven by the fuel
5 pump 30 to
the respective pilot torch nozzles 34 and the main manifold 36 in patterns
similar to those illustrated in Figures 3-6, if only the bypass with the
ecology solenoid
valve 62 and the check valve 68 are omitted. (The fluidic connection between
the
fuel flow passages 48 and 50 including the fuel flow passages 54, 56 with the
flow
equalization solenoid valve 58 remain in the system.)
10 Should both
the bypass with the ecology solenoid valve 62 and the check
valve 68 and the fluidic connection including fuel flow passages 54, 56 with
the flow
equalization solenoid valve 58 be omitted, the fuel driven by the fuel pump 30
to the
main manifold in both the processes of refilling the manifold at a low fuel
pressure
and supplying fuel to the combustor at a high fuel pressure for combustion,
are
15 directed
through the open inlet 140 and outlet 144 and the fuel flow passage 50,
similar to the step illustrated in Figure 6 (but without the additional fuel
flow through
the fuel flow passages 54, 56 which have been omitted).
In a commanded engine shutdown sequence, the fuel pump stops and the
revised pressure differential is created by the residual compressor air. In
order to
20 allow the
fuel remaining in the pilot torch nozzles 34 and the main manifold 36 to
flow back through the system to the fuel source 32, the valve 138 remains in
an open
status. The time delay between the start points of purging fuel from the pilot
torch
nozzles 34 and purging the fuel from the main manifold 36 can be achieved by
controlling the flow equalization solenoid valve 58 (if it is included in the
fuel
25 system 128)
similar to the description with reference to Figures 7 and 8, or by
controlling the time difference between opening outlets 142 and 144 of the
valve 138
during the fuel purging process (if the fluidic connection of fuel flow
passage 54, 56
with the flow equalization solenoid valve 58 are omitted).
The above description is meant to be exemplary only, and one skilled in the
30 art will
recognize that changes may be made to the embodiments described without
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CA 02847641 2014-03-27
departure from the scope of the invention disclosed. For example, the present
invention can be applied to various types of gas turbine engines other than a
turbofan
gas engine which is used as an example to illustrate the application of the
present
invention. A fuel system may include more or less components therein for
various
types of gas turbine engines without departing from the spirit of the claimed
invention, and may include but not be limited to fuel reheating devices, fuel
metering
devices, etc. The bypass controlled by the ecology solenoid valve of the
present
invention can be added to fuel systems of various types which may not include
fuel
flow passages to a pilot torch nozzle and do not allow purging of fuel from a
main
manifold of the combustor of the fuel system, in order to achieve purging of
fuel
from the main manifold of the combustor through the system via the added
bypass.
Still other modifications which fall within the scope of the present invention
will be
apparent to those skilled in the art, in light of a review of this disclosure,
and such
modifications are intended to fall within the appended claims.
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